EP2709902B1 - Heckladeflugzeug with doppelter t-leitwerkanordnung - Google Patents
Heckladeflugzeug with doppelter t-leitwerkanordnung Download PDFInfo
- Publication number
- EP2709902B1 EP2709902B1 EP11869946.1A EP11869946A EP2709902B1 EP 2709902 B1 EP2709902 B1 EP 2709902B1 EP 11869946 A EP11869946 A EP 11869946A EP 2709902 B1 EP2709902 B1 EP 2709902B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- fuselage
- aircraft
- aft
- tail
- vertical
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 239000003381 stabilizer Substances 0.000 claims description 55
- 230000008901 benefit Effects 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 239000012530 fluid Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000001141 propulsive effect Effects 0.000 description 2
- 241000566150 Pandion haliaetus Species 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/02—Tailplanes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1407—Doors; surrounding frames
- B64C1/1415—Cargo doors, e.g. incorporating ramps
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
Definitions
- This disclosure relates in general to the field of heavier-than-air aircraft, and more particularly to an aft-loading aircraft with a twin t-tail assembly.
- Aircraft designed for transporting cargo have a number features that distinguish them from passenger aircraft.
- many cargo aircraft include a high-mounted tail to allow cargo to be loaded and unloaded on an aft ramp through the rear of the aircraft.
- These aft-loading cargo ramps are often large enough to allow heavy equipment to be driven in and out the aircraft.
- H-tail and T-tail configurations have both been used for the tail assembly of aft-loading aircraft.
- the Bell-Boeing V-22 Osprey has used an H-tail
- the Boeing C-17 has used a T-tail assembly.
- An H-tail with a ramp afterbody is a structurally efficient assembly, but the vertical fins of the H-tail may be subjected to impingement from n/rev rotor wake and vortices shed from a wing-nacelle interface. This can excite horizontal tail vertical bending and can be a significant source of fuselage vibration.
- a T-tail ramp afterbody may also have significant shortcomings.
- a T-tail assembly has a single point load path for stabilizer-to-fin moments with substantial shear loading.
- a T-tail ramp assembly may require a beam across the ramp to carry fin loads, which can significantly increase weight and complexity.
- German patent application DE 10 2004 035161 A1 describes an airplane having vertical stabilizer fins arranged outside the vertical airplane symmetry plane.
- the airplane fuselage has a slim end section formed by a tail cone having upper and lower tail boards.
- the upper and lower tail boards may be simultaneously swiveled upwards and downwards, respectively, by an angle of 20 to 45 degrees relative to a horizontal plane.
- United States patent US 3,652,035 describes a twin boom lifting body fuselage aircraft having a twin tail assembly with a single horizontal stabilizer.
- a downward semicircular channel is formed in the center of the horizontal stabilizer, and an engine is mounted in the channel, with a propeller immediately adjacent a forward edge of the channel.
- United States patent application US 2009/0084889 A1 describes an aircraft the propulsive units of which include engines, a wing structure fixed to an upper region of the fuselage, and a vertical tail system having at least two vertical stabilizers which are generally vertically fixed to the fuselage aftwardly of the wing structure.
- the engines are disposed side by side in a propulsive package disposed above the fuselage.
- United States patent application US 2010/0133377 A1 describes an aircraft that includes a fuselage having a shape elongated along a longitudinal axis X of the aircraft and at least one wing fixed to the fuselage between the front end and the rear end of the fuselage.
- the fuselage includes a substantially cylindrical central part and a rear tapered part on which a vertical empennage is fixed. Between a section connecting the rear part with the central part of the fuselage and the rear end the maximum width of each section of the fuselage is constant or increasing rearwards up to a maximum width L of the fuselage, the height of each section of the fuselage is decreasing rearwards in the direction of the negative X, so that the rear end of the fuselage forms a trailing edge having a small thickness which is substantially horizontal in an aircraft reference system and substantially rectilinear.
- Aircraft 100 includes fuselage 102, wings 104a-104b, propulsion system 106a-106b, and empennage (or "tail assembly") 108.
- Tail assembly 108 generally includes twin vertical stabilizers (or "fins”) 110a-110b, a horizontal stabilizer 112, and a portion of fuselage 102 to which vertical stabilizers 110a-110b can be attached.
- Each of vertical stabilizers 110a-110b may further include a fixed portion and a movable control surface (i.e., a rudder) along each respective trailing end to control yaw.
- Horizontal stabilizer 112 may be transversely mounted to the top of each vertical stabilizer 110a-110b, and may be used to balance and share lifting loads with wings 104a-104b. Horizontal stabilizer 112 may also include a fixed lifting portion and a movable control surface (i.e., an elevator) to control pitch.
- a movable control surface i.e., an elevator
- Figure 1B is a partial rear view of aircraft 100, which further illustrates details that may be associated with one embodiment of tail assembly 108, as well as aft opening 120 and cargo door 122.
- Cargo door 122 may be movably attached to tail assembly 108 such that cargo door may be moved between a closed position and an open position to provide access through aft opening 120 into an interior cargo compartment, for example.
- Vertical stabilizers 110a-110b are generally vertical and extend upward and rearward from an internal side member (not visible in Figure 1 B) on each side of aft opening 120 (i.e., on the port and starboard sides).
- FIG 2 is a partial side view of an example embodiment of an aft-loading tail assembly 200 in accordance with this specification.
- Tail assembly 200 includes a generally cylindrical fuselage portion 202 with a tapered tail, a first vertical stabilizer 204, and a horizontal stabilizer 206 transversely attached to first vertical stabilizer 204 and a second vertical stabilizer (not visible in Figure 2 ).
- tail assembly 200 uses a semi-monocoque structure.
- Such a structure generally has interior frame members (shown in phantom) that can support a load-bearing exterior material or "skin" (e.g., sheet metal or composite material).
- Interior frame members may include, for example, formers 208a-208d (also known as “frames”) in the shape of the desired cross-section, and longitudinal stringer members 210a-210b (also known as longerons) that join formers 208a-208d together.
- a side member 212 may be rigidly attached to fuselage portion 202. Side members are fastened to one or more of stringer members 210a-210b and one or more of formers 208a-208d, particularly in the aft portion of fuselage portion 202, such as frame member 208c-208d. Side member 212 extends into vertical stabilizer 204 to transmit aerodynamic loads from vertical stabilizer 204 into fuselage portion 202.
- side member 212 can be extended generally up and toward the aft of fuselage portion 202.
- the portion of side member 212 that extends into vertical stabilizer 204 i.e., spar member 214) can be attached to rib members 216a-216b to support a skin on vertical stabilizer 204.
- Tail assembly 200 also includes a second vertical stabilizer (not visible in Figure 2 ) with a substantially similar configuration as first vertical stabilizer 204.
- FIG 3 is a partial top view of an example tail assembly 300 that illustrates additional details that may be associated with one embodiment of aircraft 100.
- Vertical stabilizers 302a-302b are generally aligned with a primary side member 304a-304b, respectively.
- the configuration of twin vertical stabilizers and a high-mounted horizontal stabilizer may form a "tail box" between the fuselage, twin vertical stabilizers, and horizontal stabilizer.
- a fluid's velocity must increase as it passes through a constriction to satisfy the principle of continuity, while its pressure must decrease to satisfy the principle of conservation of mechanical energy.
- Venturi drag can be substantially reduced or eliminated, though, by mounting a horizontal stabilizer 306 (see Figure 3 ) substantially or entirely aft of fuselage 308.
- a twin T-tail assembly can effectively extend the side structure of a cargo ramp directly into twin vertical stabilizers, creating a structurally efficient and potentially lighter weight tail configuration than found in current aft-loading aircraft.
- twin vertical stabilizer sections 402a-402b with the same thickness-to-chord ratio as a single vertical stabilizer section 404 have much less total volume than single vertical stabilizer 404.
- Figure 4 is a cross-section view of vertical stabilizer section 404, as may be found in a typical T-tail configuration, overlaid on twin vertical stabilizer sections 402a-402b that may be used in a twin T-tail configuration according to this specification.
- Vertical stabilizer total volume is a strong parametric weight indicator; thus, twin vertical stabilizer 604a-604b should be lighter than single vertical stabilizer 602, simply on a volume basis.
- twin vertical stabilizer 402a-402b can be thinner and provide equivalent stabilizer area as single vertical stabilizer 404 while reducing the overall height of the tail assembly, which can facilitate storage and servicing.
- a twin T-tail assembly 500 does not require structural beams 502 that may be required in a single T-tail assembly 504 to carry stabilizer loads out to the primary structure 506a-506b at the sides of aft opening 508, which can significantly reduce the weight and complexity of a tail assembly.
- Single point load path for horizontal-to-vertical moments and shear loads can also be reduced in twin T-tail assembly 500.
- twin vertical stabilizers such as stabilizers 602a-602b can be placed closer together than vertical stabilizers 604a-604b in a comparable H-tail configuration, which can substantially reduce or eliminate vibrations from rotor wake and vortices impinging on vertical stabilizers 604a-604b in the H-tail.
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Tires In General (AREA)
- Connection Of Plates (AREA)
Claims (7)
- Eine Flugzeugleitwerkanordnung (108; 200; 300; 500), bestehend aus:einem Rumpfteil (102; 202; 308), das über eine Hecköffnung (120; 508) mit Ladetür (122) verfügt;einer ersten (110a; 204; 302a; 402a; 602a) und einer zweiten (110b; 302b; 402b; 602b) Seitenflosse, die am Rumpfteil (102; 202; 308) angebracht ist; undeiner Höhenflosse (112; 206; 306), die quer zur ersten (110a; 204; 302a; 402a; 602a) und zweiten (110b; 302b; 402b; 602b) Seitenflosse angebracht ist;dadurch charakterisiert, dass die Vorrichtung darüberhinaus Folgendes umfasst:einen ersten Stringer (210a/210b) im Rumpfteil (102; 202; 308);einen zweiten Stringer (210b/210a) im Rumpfteil (102; 202; 308);ein erstes Seitenteil (212), das teilweise im Rumpf liegt und am ersten Stringer (210a/210b) angebracht und so gestaltet ist, dass es teilweise innerhalb der ersten Seitenflosse (110a; 204; 302a; 402a; 602a) verläuft; undein zweites Seitenteil, das teilweise im Rumpf (102; 202; 308) liegt und am zweiten Stringer (210b/210a) angebracht und so gestaltet ist, dass es teilweise innerhalb der zweiten Seitenflosse (110b; 302b; 402b; 602b) verläuft.
- Die Flugzeugleitwerkanordnung in Anspruch 1, wobei das erste (212) und zweite Seitenteil jeweils an einem inneren Rahmenteil (208a-d) des Rumpfteils (102; 202; 308) angebracht sind.
- Die Flugzeugleitwerkanordnung in Anspruch 1, wobei die Höhenflosse (112; 206; 306) im Wesentlichen am Heck des Rumpfteils (102; 202; 308) positioniert ist.
- Ein Flugzeug (100) bestehend aus:einem Rumpf (102; 202; 308), der die Flugzeugleitwerkanordnung eines der vorhergehenden Ansprüche umfasst; undTragflächen (104a, 104b), die am Rumpf (102; 202; 308) angebracht sind;wobei sich das erste Seitenteil (212) neben einer ersten Seite der Tür (122) und das zweite Seitenteil neben einer zweiten Seite der Tür (122) befindet.
- Das Flugzeug in Anspruch 4, darüberhinaus bestehend aus einem Antriebssystem (106a, 106b), das an den Tragflächen (104a, 104b) angebracht ist.
- Das Flugzeug in Anspruch 4, darüberhinaus bestehend aus einem Kipprotor-Antriebssystem, das an den Tragflächen (104a, 104b) angebracht ist.
- Das Flugzeug in Anspruch 4, wobei die erste (110a; 204; 302a; 402a; 602a) und zweite (110a; 302b; 402b; 602b) Seitenflosse nach oben und nach hinten vom Heckteil des Rumpfs (102; 202; 308) verläuft, so dass sich eine Eintrittskante der Höhenflosse (112; 206; 306) im Heck des Rumpfs (102; 202; 308) befindet.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/US2011/044937 WO2013015765A1 (en) | 2011-07-22 | 2011-07-22 | Aft-loading aircraft with-twin t-tail assembly |
Publications (3)
Publication Number | Publication Date |
---|---|
EP2709902A1 EP2709902A1 (de) | 2014-03-26 |
EP2709902A4 EP2709902A4 (de) | 2014-07-23 |
EP2709902B1 true EP2709902B1 (de) | 2015-09-02 |
Family
ID=47601385
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP11869946.1A Active EP2709902B1 (de) | 2011-07-22 | 2011-07-22 | Heckladeflugzeug with doppelter t-leitwerkanordnung |
Country Status (3)
Country | Link |
---|---|
US (1) | US9162748B2 (de) |
EP (1) | EP2709902B1 (de) |
WO (1) | WO2013015765A1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN106516081A (zh) * | 2016-11-28 | 2017-03-22 | 顺丰科技有限公司 | 一种高配平能力的水平尾翼和飞机 |
Families Citing this family (13)
Publication number | Priority date | Publication date | Assignee | Title |
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GB201011843D0 (en) * | 2010-07-14 | 2010-09-01 | Airbus Operations Ltd | Wing tip device |
EP3078586B1 (de) * | 2015-04-08 | 2018-02-21 | Airbus Operations S.L. | Flugzeugheckaufbau |
FR3040686B1 (fr) * | 2015-09-08 | 2018-09-07 | Airbus Operations Sas | Partie arriere d'aeronef comprenant un stabilisateur vertical dont la structure formant caisson comporte une partie inferieure logee dans le fuselage |
US11673643B2 (en) | 2016-03-23 | 2023-06-13 | Jp Aerospace Group, Inc. | Low stall or minimum control speed aircraft |
US10106265B2 (en) * | 2016-06-24 | 2018-10-23 | General Electric Company | Stabilizer assembly for an aircraft AFT engine |
CN106218885B (zh) * | 2016-08-06 | 2018-11-23 | 陕西沃德航空科技有限公司 | 一种倾转旋翼无人机 |
USD808328S1 (en) | 2016-09-14 | 2018-01-23 | Bell Helicopter Textron Inc. | Foldable tiltrotor aircraft |
USD974276S1 (en) | 2018-11-15 | 2023-01-03 | Textron Innovations, Inc. | Aircraft spinner |
USD974277S1 (en) | 2018-11-15 | 2023-01-03 | Textron Innovations, Inc. | Aircraft payload enclosure |
USD909949S1 (en) | 2018-11-15 | 2021-02-09 | Bell Helicopter Textron Inc. | Tiltrotor aircraft |
USD909278S1 (en) | 2018-11-15 | 2021-02-02 | Bell Helicopter Textron Inc. | Foldable tiltrotor aircraft |
CN112429199B (zh) * | 2020-11-18 | 2021-09-24 | 北京北航天宇长鹰无人机科技有限公司 | 一种采用全动升降舵的无人机 |
USD944331S1 (en) * | 2021-02-26 | 2022-02-22 | Shantou Chenghai Longman Technology Co., Ltd | Quadrotor |
Family Cites Families (17)
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US2989269A (en) * | 1959-04-06 | 1961-06-20 | Bel John P Le | Convertible aircraft |
US3409248A (en) * | 1965-10-22 | 1968-11-05 | Harvard J. Bryan | Rotary winged aircraft with drag propelling rotors and controls |
US3652035A (en) | 1969-06-12 | 1972-03-28 | Charles G Fredericks | Channel tail aircraft |
US3666211A (en) | 1970-03-12 | 1972-05-30 | Mc Donnell Douglas Corp | Trijet aircraft |
US4448372A (en) * | 1981-09-30 | 1984-05-15 | The Boeing Company | Aircraft vertical fin-fuselage structural integration system |
US6014940A (en) * | 1986-04-25 | 2000-01-18 | Jacobson; Clayton | Surface effect craft |
DE19916132C1 (de) * | 1999-04-09 | 2000-08-03 | Daimler Chrysler Aerospace | Flugzeug mit an seinem Rumpfheck angeordneten Doppelseitenleitwerk |
DE60142830D1 (de) | 2000-05-16 | 2010-09-30 | Bell Helicopter Textron Inc | Multimodales schwenkrotorgondel-steuerungssystem |
US6843447B2 (en) * | 2003-01-06 | 2005-01-18 | Brian H. Morgan | Vertical take-off and landing aircraft |
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DE102004035161B4 (de) | 2004-07-20 | 2013-09-05 | Airbus Operations Gmbh | Flugzeug mit Rumpfheck-Ladeklappen |
US7549604B2 (en) * | 2006-10-26 | 2009-06-23 | Hutterer Joseph A | Fuel efficient fixed wing aircraft |
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-
2011
- 2011-07-22 WO PCT/US2011/044937 patent/WO2013015765A1/en active Application Filing
- 2011-07-22 US US13/699,998 patent/US9162748B2/en active Active
- 2011-07-22 EP EP11869946.1A patent/EP2709902B1/de active Active
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN106516081A (zh) * | 2016-11-28 | 2017-03-22 | 顺丰科技有限公司 | 一种高配平能力的水平尾翼和飞机 |
Also Published As
Publication number | Publication date |
---|---|
US20130153708A1 (en) | 2013-06-20 |
US9162748B2 (en) | 2015-10-20 |
EP2709902A4 (de) | 2014-07-23 |
WO2013015765A1 (en) | 2013-01-31 |
EP2709902A1 (de) | 2014-03-26 |
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